Component Aerodynamics
NASA/pyCycle generic component maps provide the aerodynamic basis for fan, compressor, and turbine performance and are scaled to the engine being modeled.
turbofanmodeling.org
TurboFanModel
Real-Time Physics-Based Turbofan Modeling Framework
TurboFanModel is a real-time system-level model of modern turbofan engine behavior. The framework combines aerodynamic component maps, Brayton-cycle thermodynamics, shaft work balance, fuel control, inlet and exhaust calculations, and numerical integration of transient spool dynamics into a self-contained engine model.
Development and test environment
TurboFanLab
TurboFanLab provides real-time access to engine controls, operating conditions, spool response, fuel flow, EGT, thrust, and shaft-work relationships during model development and validation.
Modeling method
Physics first, with traceable engine definitions
Thermodynamic Cycle
Pressure, temperature, mass flow, fuel addition, turbine work, and exhaust conditions are calculated through the coupled engine flow path.
Real-Time Dynamics
HP and LP spool response is formulated with differential equations and numerical integration techniques such as fourth-order Runge–Kutta.
Traceability
Engine-definition values are identified as published, calculated, estimated, or tuned so that assumptions and validation changes remain visible.
Current demonstration
GE90-115B
The first full reference-engine demonstration is based on the GE90-115B. Publicly available GE, NASA, certification, and research data are being used to establish the master parameter set and convert the NASA/pyCycle Fan, LPC, HPC, HPT, and LPT map surfaces to GE90 design targets.
Planned validation progresses from static TurboFanLab tests to transient and altitude/Mach operation, followed by aircraft-level flight testing with a Boeing 777 model using available flight-simulation programs such as FlightGear/JSBSim.
Potential applications
One engine core, several research interfaces
Propulsion controls
Hardware-in-the-loop
Engine health / PHM
Digital-twin research
Hybrid-electric propulsion
Aircraft / propulsion studies
Flight simulation
The engine core is intended to remain independent of the host application. External interfaces can supply flight/environmental conditions and control inputs while receiving thrust, instrumentation, and detailed engine-state telemetry.
Current review material
Documents
These are interim development documents and will be revised as the GE90 component maps and validation results mature.
TurboFan_7 User Manual — Rev 1.13
Operating guide for TurboFanLab, TurboMgr, TurboModel, networking, parameters, and test workflow
TurboFanModel Framework Overview v0.2
One-page project description
GE90-115B Modeling Basis v0.1
Published data, calculations, assumptions, and modeling plan
GE90-115B Master Parameters v0.1
Working parameter and map-conversion workbook
Point of contact
Contact
Questions, research interest, or collaboration inquiries are welcome.